• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Aircraft The present invention provides an aircraft (10) with the following characteristics: the aircraft (10) comprises a spare rotor (11, 12); and the spare rotor (11, 12) can be deployed from a rest position (11) to a position of use (12). Figure to be published with the abstract: Fig. 1
    公开号:FR3083518A1
    申请号:FR1907239
    申请日:2019-07-01
    公开日:2020-01-10
    发明作者:Stefan Bender
    申请人:Dr Ing HCF Porsche AG；
    IPC主号:
    专利说明:

    Description
    Title of the invention: Aircraft The present invention relates to an aircraft, in particular a fully electric aircraft capable of taking off and landing vertically (vertical take-off and landing) The term VTOL designates in aerospace and aeronautical technique all type of airplane, drone or rocket with the capacity to take off and land again essentially vertically and without a take-off and landing runway. This generic term will be used subsequently in the broad sense including not only rigid wing airplanes with bearing surfaces but also rotorcraft such as helicopters, gyroplanes, gyrodines, and hybrids such as composite or combined helicopters as well as convertible planes.Also include aircraft with the ability to take off and land on particularly short runways (short takeoff and landing, STOL), take off on short runways but land vertically (short take-off and vertical landing, STOVL) or take off vertically but horizontally land (vertical take-off and landing horizontal, Vthl).
    Document US7677491B2 discloses an aircraft supported delivery system equipped with a self-rotating rotor system that can be deployed. The rotor system simplifies the descent control.
    A rotor that can be deployed according to document US3333643A has flexible blades and a folding structure to allow storage in a minimal space, the arrangement automatically unfolding, after release, in a partially open starting position in which the embedded wings drive the rotor during the fall due to the air current and the rotor blades being released in stages by a mechanism dependent on the speed of rotation, so that the deceleration gradually increases. When fully extended, the rotor can be controlled in terms of direction and it automatically adjusts the descent speed.
    A rotor that can be deployed according to document US4017043A can for example be used as a lifting device for an ejectable seat, the pitch of the rotor blades varying as a function of the speed of rotation.
    The invention provides an aircraft, fully electric, capable of taking off and landing vertically in the direction indicated above.
    According to the invention, the aircraft is characterized by the following characteristics:
    • the aircraft has a spare rotor; and • the emergency rotor can be deployed from a rest position to a position of use;
    • the emergency rotor can be deployed in a direction opposite to a direction of cruise flight of the aircraft;
    • the emergency rotor is disposed at a nose of the aircraft;
    • the aircraft has a fully electric drive;
    • the aircraft includes bent or bendable bearing surfaces;
    • the aircraft includes a rapidly rechargeable battery system;
    • the aircraft includes horizontally stationary blowers for take-off and landing;
    • the aircraft has slats; and • the horizontal blowers can optionally be covered using the slats;
    • the aircraft includes vertically fixed blowers to produce forward propulsion; and • the aircraft can be optionally fully autonomous.
    An advantage of this solution is the increased safety of a correspondingly equipped aircraft. In operation in regular flight, the rotor is in this case housed in a protected manner in the aircraft, preventing any avian collision.
    Other advantageous configurations of the invention are set out below. The aircraft can thus be provided with, for example, bent or even bearing surfaces which can be optionally bent. A corresponding variant enlarges the active wing surface in horizontal flight without, however, extending the surface area of the aircraft.
    The aircraft may also have a rapidly rechargeable battery system providing drive energy for vertical takeoff and landing as well as for horizontal flight and allowing rapid charging of the aircraft when stationary. .
    Instead of free-motion rotors, one can use here to drive the aircraft several blowers (ducted fans) also of different sizes, as they are known outside the field of aeronautical technique, for example in cushion vehicles air or hydrofoils. The cylindrical casing surrounding the propeller makes it possible to considerably reduce, in such an embodiment, the losses of thrust due to swirls at the ends of the blades. Suitable blowers can be oriented horizontally or vertically, can be made between the two positions or be covered by strips (louvers) in horizontal flight for aerodynamic reasons. One can also consider a purely horizontal thrust production using fixed blowers.
    Finally, it is envisaged - in addition to preferably entirely autonomous operation of the aircraft - also to entrust manual control to the human pilot in the event of sufficient qualification, which gives the device according to the invention maximum flexibility in the handling of the aircraft. gear.
    An exemplary embodiment of the invention is illustrated in the drawing and will be described in more detail below.
    [Fig.l] illustrates the top view of an aircraft.
    The single figure illustrates the construction features of a preferred embodiment of the aircraft 10 according to the invention.
    The aircraft 10 includes identifiable at the level of its nose 14 a spare rotor 11,12 which can be deployed in accordance with the illustration upwards and thus against the direction of cruise flight. While this thin spare rotor 11,12 is integrated in a substantially non-perceptible manner in its rest position 11 so as to occupy the minimum space requirement in the fuselage of the aircraft 10, it can if necessary be brought by a translational movement of about one and a half times its diameter in a position of use 12 projecting forward in front of the cockpit, outside the steering wheel. In this end position, the emergency rotor 11, 12 can be used to support or replace possible lift rotors in the event of a forced landing or to counter a stall in the event of idle cruise flight, in the event of a breakdown.
    Of course, the invention is not limited to the embodiment described and shown in the accompanying drawing. Modifications remain possible, in particular from the point of view of the constitution of the various elements or by substitution of technical equivalents, without thereby departing from the scope of protection of the invention.
    权利要求:
    Claims (1)
    [1" id="c-fr-0001]
    claims [Claim 1] Aircraft (10), characterized by the following characteristics:• the aircraft (10) comprises an emergency rotor (11, 12); and• the emergency rotor (11, 12) can be deployed from a rest position (11) to a position of use (12). [Claim 2] Aircraft (10) according to claim 1, characterized by the following characteristic:• the emergency rotor (11, 12) can be deployed in adirection opposite (13) to a direction of cruise flight of the aircraft (10). [Claim 3] Aircraft (10) according to claim 1 or 2, characterized by the following characteristic:• the emergency rotor (11, 12) is arranged at a nose (14)of the aircraft (10). [Claim 4] Aircraft (10) according to any one of claims 1 to 3, characterized by the following characteristic:• the aircraft (10) has a fully drivenelectric. [Claim 5] Aircraft (10) according to any one of claims 1 to 4, characterized by the following characteristic:• the aircraft (10) comprises angled bearing surfaces orcan be bent. [Claim 6] Aircraft (10) according to any one of claims 1 to 5, characterized by the following characteristic:• the aircraft (10) includes a battery system quicklyloadable. [Claim 7] Aircraft (10) according to any one of claims 1 to 6, ca-
    characterized by the following characteristic:• the aircraft (10) comprises horizontally stationary blowersfor takeoff and landing. [Claim 8] Aircraft (10) according to claim 7, characterized by the following characteristics:• the aircraft (10) has slats; and• the horizontal blowers can optionally be covered with slats. [Claim 9] Aircraft (10) according to any one of claims 1 to 8, characterized by the following characteristic:• the aircraft (10) includes vertically stationary blowersto produce forward propulsion. [Claim 10] Aircraft (10) according to any one of claims 1 to 9, characterized by the following characteristic:• the aircraft (10) can be optionally controlled sofully autonomous.
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    类似技术:
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    同族专利:
    公开号 | 公开日
    GB2576248B|2021-06-02|
    JP6825050B2|2021-02-03|
    DE102018116152A1|2020-01-09|
    JP2020006945A|2020-01-16|
    CN110683045A|2020-01-14|
    GB201909480D0|2019-08-14|
    US20200010185A1|2020-01-09|
    GB2576248A|2020-02-12|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    CN112046763A|2020-09-07|2020-12-08|南京航空航天大学|Multi-power-source tandem type hybrid unmanned aerial vehicle and control method thereof|US2497590A|1946-04-12|1950-02-14|Emma M Drill|Emergency plane carrier|
    DE1136580B|1960-10-01|1962-09-13|Boelkow Entwicklungen Kg|Rotary wing aircraft|
    US3333643A|1965-03-16|1967-08-01|Ryan Aeronautical Co|Flexible deployable rotor system|
    US3529793A|1969-03-27|1970-09-22|Zaharias Krongos|Airplane with emergency propeller and detachable wings|
    US3693910A|1970-12-14|1972-09-26|Angelo J Aldi|Aircraft rotor blade mechanism|
    US3900176A|1973-05-31|1975-08-19|Robert A Everett|Aircraft|
    US4017043A|1976-03-08|1977-04-12|The United States Of America As Represented By The Secretary Of The Navy|Deployable rotor|
    DE3240995A1|1982-11-03|1984-05-03|Hoffmann Fluzeugbau Friesach GmbH, 9322 Friesach|Motor-glider|
    JPS61140800A|1984-12-11|1986-06-27|Nec Corp|Missile|
    DE4420219A1|1994-06-06|1995-12-07|Stemme Gmbh & Co Kg|Fixed wing aircraft with two coaxial propellers of different diameters|
    DE10040577B4|2000-08-18|2006-02-23|König, Helmut, Ing.|Drive device for aircraft|
    DE20303024U1|2002-09-06|2003-08-14|Hinueber Edgar V|Combination aircraft has rotor lift for telescoping of rotor power unit and makes it possible for rotor drive to be withdrawn completely from aerodynamic influence in plane flying by recessing into fuselage or to extend it from fuselage|
    US7677491B2|2005-08-05|2010-03-16|Raytheon Company|Methods and apparatus for airborne systems|
    US20100072325A1|2008-01-22|2010-03-25|Kenneth William Sambell|Forward Folding Rotor for a Vertical or Short Take-Off and Landing Aircraft|
    DE202010016892U1|2010-12-21|2011-08-26|Walter Pahling|Amphibious ultralight aircraft of recent design|
    US8967529B1|2011-03-25|2015-03-03|Odyssian Technology, Llc|Battery-structure|
    DE102011105880B4|2011-06-14|2014-05-08|Eads Deutschland Gmbh|Electric drive device for an aircraft|
    US9786961B2|2011-07-25|2017-10-10|Lightening Energy|Rapid charging electric vehicle and method and apparatus for rapid charging|
    DE102012010937B4|2012-06-01|2020-10-01|Emt Ingenieurgesellschaft Dipl.-Ing. Hartmut Euer Mbh|Aircraft|
    JP2017528355A|2014-06-03|2017-09-28|アヨロア フアン，クルス|High performance vertical take-off and landing aircraft|
    DE102014213215A1|2014-07-08|2016-01-14|Lilium GmbH|whiz|
    EP3399381A1|2014-09-05|2018-11-07|SZ DJI Technology Co., Ltd.|Context-based flight mode selection|
    DE202015003815U1|2015-05-27|2015-07-22|Maximilian Salbaum|Vertical launching and landing aircraft with electric ducted propellers|
    US10889385B2|2015-09-11|2021-01-12|Bombardier Inc.|Apparatus and methods for distributing electric power on an aircraft during a limited power availability condition|
    DE202015007089U1|2015-10-10|2015-11-12|Maximilian Salbaum|Launching and landing vertically blended wing body aircraft with electric ducted propellers|
    DE102015121744B4|2015-12-14|2021-12-16|Hans Ulrich Tobuschat|Propulsion device for a missile|
    CA2934346A1|2016-06-29|2017-12-29|William C. Bailie|Short take off and landing arial vehicle|
    KR101938459B1|2016-12-15|2019-01-14|한국항공우주연구원|Aircraft|
    DE202018000856U1|2018-02-19|2018-03-06|Christian Danz|Protection system for flight systems|DE102020113489A1|2020-05-19|2021-11-25|Dr. Ing. H.C. F. Porsche Aktiengesellschaft|Aircraft|
    DE102020113490A1|2020-05-19|2021-11-25|Dr. Ing. H.C. F. Porsche Aktiengesellschaft|Aircraft|
    法律状态:
    2020-07-22| PLFP| Fee payment|Year of fee payment: 2 |
    2021-07-28| PLFP| Fee payment|Year of fee payment: 3 |
    2021-10-15| PLSC| Publication of the preliminary search report|Effective date: 20211015 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018116152.2A|DE102018116152A1|2018-07-04|2018-07-04|aircraft|
    DE102018116152.2|2018-07-04|
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